Supercharging multipower system



Jan. 12, 1932. A, c PETERSON 1,841,149

SUPERCHARGING MULTIPOWER SYSTEM Filed June 7, 1929 2 Sheets-Sheet l Jan.12, 1932. A c R O 1,841,149

SUPERCHARGING MULTIPOWER SYSTEM Filed June '7, 1929 2 Sheets-Sheet 2Patented Jafn. 12 1932 ADOLPEE. c. PETERSON, or

PATENT OFFICE MINNEAPOI LI S, MINNESOTA surnncisu'lmtime n un'r rownnSYSTEM Application filed June 7,

My invention relates to power systems for aeroplanes and has certainparticular features wherefore it is called a supercharging multi-powersystem. The principal objects of my invention are to provide a powersystem for aeroplanes which shall be simple in construction, reliable inuse and which shall be light in weight while having ruggedness anddurability. A printrate my invention like characters refer to like partsthroughout the several views. The r principal devices and combinationsof devices cipal object is to I provide a power systemzfor ,such'usewhich shall by reason of its simplicity be more free from fault andfailure, and which by'reason of its method of construction andadaptation to the aeroplane shall be relatively more light in weight andstronger in construction. An object is to providea power system whichshall have espe cial characteristics regarding the charging with air andfuel. In general the object is to provide an improved and simplifiedpower system for aeroplane use.

In the accompanying drawings which illuscomp'risi g my, invention areas-hereinafter described and asdefined in the claims,

Figure 1 is a view-chiefly in plan, some of i the parts being inhorizontal section on the line I .I of Figure-2 and some of the partsnotably the wing covering being removed for the sake of clearness in theillustration of the particular features,

' Figure 2 is a view in vertical section on the line 11-11 of Figure 1showing especially the cross section' ofthe wing and the enginemounting.

Figure 3 is a view in cross section transverse to that of Figure 2, thissection being a vertical section on the line IIIIII of Figures 1 and 2,it being noted that a similar section through any of the engines is thesame.

Figure 4 shows a modified mounting. Referring again to the drawings, thenumeral 1 indicates a fuselage or a sea-plane hull to which my vdeviceis applied, this hull or fuselage being shown relatively slender in itswidth inorder to better illustrate the remaining parts. The hull 1(so-called here inaftcrfor brevity) has a monoplane wing 1929. SerialNo. 369,253.

which is of a truss form or box girder form and has in that portion ofits length near the hull 1 a cross section substantially square andhaving at the four corners of the square the four members 4 each ofwhich may be of angle steel or duralumin or of T section or othersection individually. The box section type spar or beam 3 forms amounting for the engines and also forms the spar of the monoplane' wingand there are mounted in this box section beam 3 four engine crankcases, each denoted 5. The crank cases are constructed preferablyof'duralumin or other light metal and they have such form that they arereadily mounted within the four members of the box' type spar and sothat they contribute also to the strength of the box section spar 3. 7

Each engine crank case 5 has a crank shaft 6 individually related to itand each crank shaft 7 has an individuall related ratchet 8v throughwhich the individ ual crank shaft is adapted to impart driving torque toits related individual mitre/gear 9 and through the latter to one of twomitre gears 10 and 11, respectively, one of the latter driving apropeller shaft 12 and the other driving a propeller shaft 13. Thepropeller shafts 12, 13 drive propellers 14, 15, respectively. Theratchets 8 are each of such construction that they will procureengagement of the related engine with the propeller shaft related onlyin driving torque of the related engine exerted in the direction drivingthe related propeller forwardly. There are four engines each pair of twodriving one propeller 14 or 15 and thus each pair of engines must haveone having crank shaft rotation one way and one having crank shaftrotation the other way. 1

Each engine crank-case 5 has secured to it on its forward side, that isthe side directed to the leading edge of the wing, cylinders 16, therebeing two or more of such cylinders in each engine. Qnly two areshown'in each for simplicity in illustration. The cylinders 16 liewiththeir longitudinal axes substantially horizontal and in a singlehorizontal plane. Each cylinder 16 has an injection nozzle 17,diagrammatically shown and a related fuel conduit 18 to feed the nozzle17, and the related engine has a fuel pump and distributor unit 19secured on the engine and adapted to be driven by the engine crankshaft. The connections or driving of the fuel distributor and pump bythe engine crank shaft is not-specifically shown-since this is notinvolved in the invention and ma be of any type.

. ach cylinder 16 has related to it and enclosing it"a cylindrical airconduit chamber 20.which lies also horizontally and is directedforwardly from the .crank case 5. Within each air conduit chamber 20 anddisposed between its inner wall and the exterior wall of therelatedcylinder 16 there are cooling fins 21 fixed to the cylinder wallwhereby air passingthrough the air conduit chamber 20 will cool thecylinders 16.

means directed to the leading edge of the- -wing and this gatheringmeans is normally open to theatmosphere as shown so that air may flowbackwardly through theair conduit chamber in flight of the aeroplane.Each air conduit chamber 20 near its rear end is free from the fins andconstitutes a small collecting chamber adjacent to a. pair 1 of airinlet ports 23 located on the sides of the cylinder 16 substantially ata height such that the pair of air inlet ports 23 will be uncovered bythe piston ofthe cylinder wheii at its outermost position and whenpassing through the induction and expulsion or exhaust portion of the.cycle.

Each cylinder 16 has also substantially on the same cross-sectionalplane as that occupied by the air inlet ports a pair of exhaust ports 24one on the lower and one on the upper side of the cylinder 16. The airinlet ports 23 are open to the air conduit chamber but the exhaust portsare not but are open to the atmosphere as shown the exhaust portsdelivering. by short individual, conduits 25 through the wing covering.

The funnels or nozzles 22 at their extreme forward end, that is at theiropen mouths may be closed by shutter valves 26 which aremanually-controlled and slide along the inside or outside of the leadingedge 'of the wing so as to. close the funnels. There is preferably oneshutter 26 for each engine adapted to close the "funnels of that engine.

g The funnels 22 may each receive air under low pressure sav five or tenpounds from J Thus each cylinder is exhausted and charged conduits 27passingalong the side of the funnels from a Roots blower or other typeair blower or compressor 28 located in the hull 1 and driven by anindependent engine 29. The engine 29 may be only a small engine adaptedto drive the blower for ashort time on starting and landing or it may bean eir gine having connection with an independent propeller. It iscontemplated that blower 28 will draw air from atmosphere and compressto five or ten pounds, and that when not operating air cannot passthrough the blower vfrom the funnels, by reasonof the construction ofthe blower but light flap valves may be interposed in the conduits 27 toprevent return flow.

In theuse of my device it is contemplated that each fuel pump anddistributor .unit receives liquid fuel from any containers in the.aeroplane and that the engines will preferably operate on the Dieselprinciple, but not necessari-1y so, and that each engine will have itsseparate starting means or that means will be provided whereby eachengine may be separately started.- In starting. the auxiliary engine29is first started and drives blower 28 and the shutters 26 are closed sothat the funnels and air conduit chambers are closed at the front end tothe atmosphere so that the blower 28 may then fill the funnels andconduits with air under five or ten pounds pres: sure. The engines arethen started and the fuel distributors distribute fueI to each cylinder,each engine having its own timing, and

thus the engines receive air from the compressor 28 and each operates asa two cycle engine and the plane may then be released and go on its way.When in the a'fn and having a substantial speed, or when given a divingor descending angle the plane will gather high speed, and thereupon theshutters 26 may be 1 opened to open funnels-22 to atmosphere at theirends or months. These mouths as shown are in the leading edges of thewing, and the plane having high speedair will be gathered in the funnelsand forced under pressure backwardly through the air conduit chambersand thence at each opening of air inlet ports in a cylinder willpass'into the cylinder and be directed by the conformation of therelated piston head tothe head of the cylinder and will assist inblowing the exhaust out of the exhaust ports to atmosphere from thelower and upper side of the wing, the airwill continue to flow duringthe entire periodat which vthe airinlet ports are open in a cylinder andlis thus there will be some-supercharging of the cylinder with air. Theair inlet ports may be made of such lengthv that they remain openslightly longer than the exhaust ports for this purpose. (Or positivelyacting port controlling means actuated by the crank shaft may beprovided to better control the charging) with fresh air under lowpressure which is compressed and subsequentl combustion follows? ,Eachfunnel or nozz e may have such shape as to contribute to the creatin ofair pressure. It is contemplated that 1n hi h speed aeroplanes this airpressure created %y the nozzles will be amply sufficient to create thecharging air pressure. Any means may be provided for charging, onstarting, other than that shown; It is contemplatedthat part i of theair from the nozzles may 0001 and onl a partflow-into the air inletports but pre erably the more simple construction is used.

Figure 4 shows a modified form of mounting of the engines, the structureof spar A in this form constitutes also a crank case for the individualengines thespar being formed of metal welded or united in the shapeshown,

- combinations'of devices'in the illustration of my device I contemplatethat other detailed devices and combinations of devicesma be used in therealization 0% my device wit out departing from the spiri andcontemplation thereof.

lVhat I claim is:

1. Inan airplaneefigine system, wings, supporting spars in the wing, anengine crank case supported longitudinally in the spars, cylindersattached to the crank case i and directed forwardly from the spar, finson the cylinders, in connection 'with surfaces of the wing tdisposed' todirect cooling air along. the fiIlSr g '2. In an airplane engine system,wings,

supporting spars in the wings, an engine crank case supportedlongitudinally in the spars, cylinders attached to the crank caseanddirected forwardly from the spar in the leading edge of the wing,cooling fins on the cylinders, and means whereby the engine propels theairplanepropellen 3. In an airplane system, wings, supporting's'pars inthe wing, a pluraht'yyof engine a ,crank cases supported longitudinallyin the tached and directed forwardl from the spars in the leading edgeof'the wing, coolin'g fins on the cylinders, and means whereby theengine propels the airplane propeller.

4. n an airplane engine system, wings,

supporting spars in the wing, a plurality of engine crank casessupported longitudinally in the spars, each crank casehaving cylinders.

. attached and directed forwardly from the spars in'the leading edge ofthe wing,cooling fins on the cylinders, and chambers spars, each crankcase having cylinders at ,Texhaust ports' i disposed in the leadin edgeof the wing for direction of air from t e leading edge of the wing tothe individual cylinders.

5. In an airplane engine system, wings, supporting spars in the wing, aplurality of engine crank cases supported longitudinally in the spars,each crank case having cylinders attached and directed forwardly fromthe spars in the leading edge of the wing, coolin fins on the cylinders,and chambers dispose in the leadin edge of the wing for direction of airfrom t e leading edge of the wing fins of the cylinders, thence to airpoc thence as controlled by the engine pistons through ports into thecylinder exhaust occurring through exhaust ports of the cylinders to theatmosphere.

6- In an airplane engine system, wings supporting spars in the wing, aplurality of engines mounted with their crank shafts longitudinally inthe spars, cylinders directed forwardly from the spars in the leadingedge of the wing. cooling fins on the cylinders, and means whereby thecrank shafts drive a propeller means. I

' 7. In an airplane engine system, a wing supporting means, an enginehaving individual engine cylinders directed forwardly in the directionof the flight of the airplane, air

gathering means directing air encountered .iu the forward flight to eachengine cylinder for the cooling thereof.

8. In an'arrplane engrne system, a wing supporting means, an'enginehaving individual engine cylinders directed forwardly in the directionof the flight of the airplane, air gathering means directing airencountered in the forward flight to each en ine' cylinder for thecooling thereof and thence to air chambers through inlet portsin theengine cylinders as governed by the engine pistons and thence throughthe exhaust ports of the enginejcylinders.

9. In an airplane engine system, wing supporting means, an engine havingindividual engine cylinders directed forwardly in the direction of theflight of the airplane, air

' gathering means directing air encountered in the forward flight toeach engine cylinder for the cooling thereof, and thence to air chambersand through inlet ports to the engine cylinders and thence thro'ughtheengine 10. An airplane engine system, wing supporting means, an enginehaving, individual cylinders diredted forwardly in the direction 7 ofthe flight of the airplane, air gathering means directing airencountered in the forward flight of the airplane to each engine 5 Hcylinder for the cooling thereof, and thence to air chambers and throughinlet ports to a the engine cylinders, means whereby the air means maybe operated to blowair to the iharging does not suflice.

12. Awing spar comprising a box girder horizontallysubstantially placedin the wing as its supporting spar, a section of the box girder having asize sufficent for and place-' ment for the revolution of an .enginecrank shaft, cylinders related and attached ,to the, spar, pistonscooperating with the crank shaft to drive the propeller shaft of theairplane. p

13, The novel means in claim 12 and air gathering means for eachcylinder receiving air from the leading edge, of the wing for cooling. IJ

14. The novel means in claim 12 and air gathering means for eachcylinder receiving air 'from the leading edge of the wing for coolingand means directing the air after cooling to the engine cylinderforcharging.

15. An airplane having an air gathering means receiving air encounteredin flight, in combination with a plurality of engines each adapted to benormally chargedin its combustion chambers for combustion of fuel by airfrom the air gathering means, means related to each engine for deliveryof fuel for combustion in its combustion chambers, and a supplementaryair' charging means power driven by auxiliary power means, for aircharging in conditions wherein normal charging does not suifice. I

16. In an airplane, an engine having cyllnders and cooperating pistonsdriving a ro eller an air atherin means havin B b forwardly directedmouth means receiving air in flight, inlet and'exhaust ports for eachcylinder whereby the" cylinder may be charged periodically by air fromthe air gathering means for combustion in the two cycle manner, andmeans for the introduction of fuel periodically to each cylinder.

'17.In an airplane, an engine having cylinders and cooperating pistonsdriving a propeller, an air gathering means having forwardly directedmouth means receiving air in flight, inlet and exhaust portsfor eachcylin- :ler whereby the cylinder may be charged periodically by airfromthe air gathering means for a combustion in the two cycle manner, meansfor the introduction of fuel period'i cally to each cylinder, and asupplementary air charging means power driven by auxiliary power meansfor air charging in condi'- tions wherein normal charging does not suf-18. In an aiplane, an engine having cylpropeller, an air gathering meanshaving forwardly directed mouth means receiving air in flight,eachcylinder having a related inlet port governed to admit air to'itscylinderduring a charging period, each cylinder having a relatedexhaustport governed to exhaust products of combustion during the chargingperiod, and means for the introduction offuel periodically to eachcylinder.

19. In an airplane, anengine having cylinders and cooperating pistonsdriving a propeller, an air gathering means having for- Wardl directedmouth means receiving air in flig t, each cylinder having a relatedinlet port governed to admit air to its cylinder during a chargingperiod, each cylinder having a related exhaust port. governed to exhaustproducts of combustion during the charging period, means for theintroduction of fuel periodically to each cylinder, and a supplementaryair charging means power driven by auxiliary power means for aircharging in conditions wherein normal charging is not operative.

20. In air airplane, a plurality of engines each having cylinders andcooperat'ing'pistons driving a propeller, an air gathering means havingforwardly directed mouth means receivingair in flight, each cylinderhaving a related inlet port governed to admit air to its cylinder duringacharging period,

each cylinder having a related exhaust port governed to exhaust productsof combustion during thecharging period, means for the introduction offuel periodically to each cylinder, and a supplementary air chargingmeans power drlven by auxiliary power means for air charging inconditions wherein normaPcharging is not operative.

In witness whereof I have hereunto set my hand this 3d day of December,1928.

ADOLPHE PETERSON.

